Aero-engine low-pressure turbine shaft radial carbon seal moving ring dismounting tool

Abstract

The utility model discloses an aero-engine low-pressure turbine shaft radial carbon seal moving ring dismounting tool, and relates to the field of aero-engine maintenance tools, a low-pressure turbine disc groove is formed in the center of the interior of a low-pressure turbine disc, a connecting flange is arranged in the low-pressure turbine disc groove, and the connecting flange is connected with the low-pressure turbine disc groove. A low-pressure turbine disc front shaft is arranged in the center of the interior of the connecting flange, the outer diameter of the turbine disc front shaft is sleeved with a radial carbon sealing movable ring, the drawing force bearing ring is formed by butt joint of the end faces of two semicircular ring plates, and the upper ring face of the drawing force bearing ring makes contact with the lower end face of the radial carbon sealing movable ring. The drawing force of the two pulling claws is evenly transmitted to the radial carbon sealing movable ring through the drawing force bearing ring, stress concentration can be effectively avoided, the risk of damage to the carbon sealing movable ring is reduced, a gap is kept between the inner edge of the drawing force bearing ring and the front shaft of the low-pressure turbine disc in the radial direction, the front shaft of the low-pressure turbine disc is prevented from being damaged in the drawing process, and the service life of the low-pressure turbine disc is prolonged. And the safety and the reliability of the dismounting operation are improved.

Description

TECHNICAL FIELD

[0001] The utility model relates to the field of aero-engine maintenance tool, concretely relates to a kind of aero-engine low-pressure turbine shaft radial carbon seal dynamic ring dismounting tool. BACKGROUND

[0002] Aero-engine low-pressure turbine shaft radial carbon seal device directly influences engine overall performance.Low-pressure turbine shaft radial carbon seal device belongs to dynamic seal structure, that is, it forms seal by using graphite ring (the core component of carbon seal static ring assembly) and radial carbon seal dynamic ring relative motion in oil medium.Practice shows that under high temperature, high pressure and high speed conditions, radial carbon seal has small leakage and long service life, and has reliable sealing performance.

[0003] Low-pressure turbine shaft radial carbon seal device is installed in low-pressure shaft rear bearing seat.Graphite ring is a kind of soft material with lubricating function, and it rotates at high speed in oil medium with radial carbon seal dynamic ring to prevent oil leakage, while ensuring that carbon seal dynamic ring is not damaged, so that graphite ring and carbon seal dynamic ring maintain constant gap in radial direction;Because the increase of gap will cause the increase of oil leakage, and then affect engine thrust and unit fuel consumption.Therefore, during maintenance and dismounting, carbon seal dynamic ring must not be damaged.Carbon seal dynamic ring is tightly installed in the bottom of low-pressure turbine disc front shaft with interference fit, and the space of low-pressure turbine disc groove structure is narrow, as shown in FIG. Figure One Therefore, the difficulty and risk of dismounting work are greatly increased.

[0004] In the prior art, it is often difficult to safely and efficiently dismount carbon seal dynamic ring from low-pressure turbine disc front shaft using ordinary claw extractor, and carbon seal dynamic ring or turbine disc front shaft is easily damaged.The utility model introduces a new type of carbon seal dynamic ring dismounting device, which realizes uniform and accurate positioning and efficient dismounting of radial carbon seal dynamic ring by combining claw extractor.The dismounting device is made of 45 steel, and its structure mainly consists of drawing force ring and fan-shaped connecting ring, which can effectively avoid stress concentration and reduce the risk of damage to carbon seal dynamic ring. CONTENT OF UTILITY MODEL

[0005] To solve the above technical problems, an aero-engine low-pressure turbine shaft radial carbon seal dynamic ring dismounting tool is provided, which solves the problem of easy damage to carbon seal dynamic ring or turbine disc front shaft in the above background technology.

[0006] An aero-engine low-pressure turbine shaft radial carbon sealing dynamic ring dismounting tool, comprising a low-pressure turbine disc, a low-pressure turbine disc groove is formed at the inner center of the low-pressure turbine disc, a connecting flange is arranged in the low-pressure turbine disc groove, a low-pressure turbine disc front shaft is arranged at the inner center of the connecting flange, a radial carbon sealing dynamic ring is sleeved on the outer diameter of the low-pressure turbine disc front shaft, a circular pressure bearing flat plate is abutted at the top end of the shaft surface of the low-pressure turbine disc front shaft, two jaw pullers are abutted at the top end of the outer surface of the circular pressure bearing flat plate, a pulling force bearing ring is sleeved on the shaft surface of the low-pressure turbine disc groove, M5 internal hexagonal cylindrical head screws are inserted into the insertion slots of the pulling force bearing ring, and fan-shaped connecting rings are installed at the connecting positions of the outer surfaces of the pulling force bearing ring.

[0007] Preferably, the two-jaw puller comprises a hexagonal head screw rod, a base and a pressure rod, the outer surface bottom end of the hexagonal head screw rod is provided with the pressure rod, the shaft surface of the pressure rod is penetrated and installed with the base, the shaft surface bottom end of the pressure rod is connected with the circular pressure bearing flat plate, and the outer surface of the base is provided with a notch.

[0008] Preferably, the two-jaw puller further comprises a puller and a bolt, the outer surface of the base is provided with a notch, the notch of the base is provided with the puller, the outer surface front end of the base is provided with the bolt opposite to the puller, the bottom end of the bolt is penetrated and installed with a plug rod, and the plug rod is penetrated and installed with the puller.

[0009] Preferably, the pulling force bearing ring is composed of two semicircular ring plates, each semicircular ring plate has two ends, and each end has two M5 internal hexagonal cylindrical head screw thread through holes, so that a total of four M5 internal hexagonal cylindrical head screw thread through holes are arranged, the end faces of the two semicircular ring plates are abutted to form the pulling force bearing ring, and a total of eight M5 internal hexagonal cylindrical head screw thread through holes are arranged.

[0010] Preferably, the fan-shaped connecting ring is a fan ring plate, and a total of two fan-shaped connecting rings are uniformly distributed along the circumferences, each fan-shaped connecting ring has four M5 internal hexagonal cylindrical head screw thread through holes, the hole distance of the fan-shaped connecting ring is the same as that of the pulling force bearing ring, and a total of eight M5 internal hexagonal cylindrical head screws are used for connecting and fixing the fan-shaped connecting ring and the pulling force bearing ring.

[0011] Preferably, the inner side radius of the fan-shaped connecting ring is R20.5, the outer side radius of the fan-shaped connecting ring is R28, the inner side radius of the pulling force bearing ring is R18.95, the outer side radius of the pulling force bearing ring is R25.95, and the radius of the connecting position between the outer surface of the pulling force bearing ring and the fan-shaped connecting ring is R27.95.

[0012] Compared with the prior art, the aero-engine low-pressure turbine shaft radial carbon sealing dynamic ring dismounting tool has the following beneficial effects:

[0013] The aviation engine low-pressure turbine shaft radial carbon sealing dynamic ring dismounting tool provided by the scheme has the advantages that the M5 inner hexagonal cylindrical head screw is connected and fixed, the structure is simple, installation is convenient, the dependence on the skills of the operators is reduced, and the labor intensity is reduced;

[0014] The two semicircular ring plate end faces are butted to form a drawing force ring, the upper ring surface of the drawing force ring is in contact with the lower end surface of the radial carbon sealing dynamic ring, the drawing force of the two draw claws is evenly transmitted to the radial carbon sealing dynamic ring through the drawing force ring, stress concentration can be effectively avoided, and the risk of damage to the carbon sealing dynamic ring is reduced;

[0015] The inner edge of the drawing force ring and the low-pressure turbine disc front shaft keep a gap in the radial direction, damage to the low-pressure turbine disc front shaft during the drawing process is avoided, and the safety and reliability of the dismounting operation are improved;

[0016] The tool is easy to manufacture and maintain, has low cost, and has good popularization and application prospect. The tool is easy to manufacture and maintain, has low cost, and has good popularization and application prospect. BRIEF DESCRIPTION OF DRAWINGS

[0017] Figure 1 It is a structural schematic view of the utility model;

[0018] Figure 2 It is a structural schematic view of the utility model;

[0019] Figure 3 It is a structural schematic view of the utility model;

[0020] Figure 4 It is a structural schematic view of the utility model;

[0021] Figure 5 It is a structural schematic view of the utility model.

[0022] Reference numerals in the drawing are:

[0023] 1, low-pressure turbine disc; 2, low-pressure turbine disc groove; 3, radial carbon sealing dynamic ring; 4, low-pressure turbine disc front shaft; 5, two-claw draw claw device; 6, circular pressure plate; 7, connecting flange; 8, drawing force ring; 9, fan-shaped connecting ring; 10, M5 inner hexagonal cylindrical head screw; 51, hexagonal head screw; 52, base; 53, draw claw; 54, bolt; 55, pressing rod. DETAILED DESCRIPTION

[0024] The following description is used to disclose the utility model so that those skilled in the art can implement the utility model. The preferred embodiments in the following description are only as examples, and other obvious modifications can be thought of by those skilled in the art.

[0025] Referring to Figures 1-5 As shown in the figure, a low-pressure turbine shaft radial carbon sealing ring dismounting tool of an aero-engine, comprising a low-pressure turbine disc 1, as the basic support part of the whole assembly, bearing all other components, a low-pressure turbine disc groove 2 is opened at the inner center of the low-pressure turbine disc 1, a connecting flange 7 is arranged inside the low-pressure turbine disc groove 2, which mainly functions to fix and cooperate with the front-stage turbine disc. But its installation position and caliber size limit the effective space inside the turbine disc groove 2, increasing the difficulty of dismounting the radial carbon sealing ring, a low-pressure turbine disc front shaft 4 is arranged at the inner center of the connecting flange 7, responsible for transmitting torque and load, at the same time, the design of this component also affects the stability of the overall structure. The outer diameter of the turbine disc front shaft 4 is sleeved with a radial carbon sealing ring, which is the core component of the dismounting tool, plays a sealing role, ensures the oil sealing of the carbon sealing static ring assembly sleeved outside the radial carbon sealing ring, the top end of the shaft surface of the low-pressure turbine disc front shaft 4 abuts against a circular pressure-bearing flat plate 6, the top end of which abuts against the low-pressure turbine disc front shaft 4, so that the downward pressure during disassembly is converted into upward pulling force on the pulling force ring and the radial carbon sealing ring by the claw puller. The outer surface top end of the circular pressure-bearing flat plate 6 abuts against two claw pullers 5, the shaft surface of the low-pressure turbine disc groove 2 is sleeved with a pulling force ring 8, an M5 internal hexagonal cylindrical head screw 10 is inserted into the slot of the pulling force ring 8, and a fan-shaped connecting ring 9 is installed at the connecting position of the outer surface of the pulling force ring 8.

[0026] The two-jaw puller 5 comprises a hexagonal head screw rod 51, a base 52 and a pressure rod 55, the outer surface of the hexagonal head screw rod 51 is provided at the bottom end with the pressure rod 55, the two-jaw puller 8 is a commonly used tool in mechanical maintenance, mainly used for disassembling the bearing or shaft sleeve from the shaft along the axial direction, and the structure is usually composed of a hexagonal head screw rod 51, a puller 53 and a base 52. The hexagonal head screw rod 51 is composed of a hexagonal rotating handle and a pressure rod 55, and rotating the pressure rod 55 can provide the puller 53 with axial movement; the puller 53 is the part directly in contact with the puller bearing ring 8, and the axial movement is transmitted to the radial carbon sealing dynamic ring 3; the base 52 is the mounting seat of the pressure rod 55 and the puller 53, and the puller bearing ring 8 is indirectly connected to the radial carbon sealing dynamic ring 3 through the puller, and the radial carbon sealing dynamic ring 3 is disassembled from the low-pressure turbine disk front shaft 4 along the axial direction, realizing uniform and accurate positioning and efficient disassembly of the radial carbon sealing dynamic ring 3, and avoiding damage to the radial carbon sealing dynamic ring 3 and the low-pressure turbine front shaft 4, the shaft surface of the pressure rod 55 is provided with the base 52, and the bottom end of the shaft surface of the pressure rod 55 is provided with a circular pressure bearing plate 6, and the outer surface of the base 52 is provided with a notch, the two-jaw puller 5 further comprises a puller 53 and a bolt 54, and the outer surface of the base 52 is provided with a notch, the notch of the base 52 is provided with the puller 53, and the outer surface of the base 52 is provided with the bolt 54 opposite to the puller 53, and the bottom end of the bolt 54 is provided with a plug rod penetrating through the base 52.

[0027] Further, the puller bearing ring 8 is composed of two half circular ring plates, each half circular ring plate has two ends, a total of four M5 internal hexagonal cylindrical head screw holes 10, and the two half circular ring plates are connected to form the puller bearing ring 8, a total of eight M5 internal hexagonal cylindrical head screw holes 10, the fan-shaped connecting ring 9 is a fan ring plate, a total of two, each fan-shaped connecting ring 9 is uniformly distributed with four M5 internal hexagonal cylindrical head screw holes 10 along the circumferential direction, the hole distance is the same as that of the puller bearing ring 8, the M5 internal hexagonal cylindrical head screw 10 is an internal hexagonal cylindrical head screw, a total of eight, used for connecting and fixing the fan-shaped connecting ring 9 and the puller bearing ring 8, the M5 screws on the left and right sides of the connection between the two half circular ring plates can be slightly increased in distance, so that the two pullers 53 of the two-jaw puller 5 can be clamped into the connection between the two half circular ring plates of the lower ring surface of the puller bearing ring 8, due to the connection and fixation of the two fan ring plates and the structural reinforcement, this place is the force point of the pulling force, which can ensure that the deformation of the puller bearing ring 8 is minimized, effectively avoid damage to the radial carbon sealing dynamic ring 3 and the low-pressure turbine disk front shaft 4 caused by the deformation of the puller bearing ring 8, improve the safety and reliability of the disassembly operation, and further reduce the accident rate caused by improper operation.

[0028] The inner radius of the fan-shaped connecting ring 9 is set as R20.5, the outer radius of the fan-shaped connecting ring 9 is set as R28, the inner radius of the drawing force bearing ring 8 is set as R18.95, the outer radius of the drawing force bearing ring 8 is set as R25.95, and the radius of the connection between the outer surface of the drawing force bearing ring 8 and the fan-shaped connecting ring 9 is set as R27.95.

[0029] Working principle and implementation: firstly, the two semicircular ring plates are placed in the low-pressure turbine disc groove 2 under the radial carbon sealing dynamic ring 3, and are butted to form the drawing force bearing ring 8 around the low-pressure turbine disc front shaft 4, the inner edge of the drawing force bearing ring 8 keeps a gap with the low-pressure turbine disc front shaft 4 in the radial direction, so as to avoid damaging the low-pressure turbine disc front shaft 4 in the drawing process; the drawing force bearing ring 8 composed of two semicircular ring plates is connected and fixed by eight M5 inner hexagonal cylindrical head screws 10 and two fan-shaped ring plates 9; then the two clamping jaws 53 of the two-jaw drawing jaw device 5 are clamped at the connection of the two semicircular ring plates of the drawing force bearing ring 4, so that the clamping jaws exert a drawing force at this position, which can ensure that the deformation amount of the drawing force bearing ring 8 is minimum; then the rotating handle of the hexagonal head screw 51 is rotated clockwise to adjust the screw rod, so that the head of the screw rod is in contact with the circular pressure bearing plate 6 placed on the end surface of the low-pressure turbine disc front shaft 4; after that, the hexagonal head screw 51 is continuously rotated to continuously exert pressure on the circular pressure bearing plate 6, and the reaction force of the circular pressure bearing plate 6 is transmitted to the drawing force bearing ring 8 through the two clamping jaws 53, so that the drawing force bearing ring 8 generates upward drawing force on the radial carbon sealing dynamic ring 3; the hexagonal head screw 51 generates a distance of 0.8mm screw pitch in the axial direction every rotation, so that the drawing force bearing ring 8 drives the radial carbon sealing dynamic ring 3 to rise by 0.8mm; the hexagonal head screw 51 is continuously rotated until the radial carbon sealing dynamic ring 3 is separated from the low-pressure turbine disc front shaft 4, and the disassembly is completed.

[0030] The basic principle, main features and advantages of the utility model are shown and described above. It should be understood by those skilled in the art that the utility model is not limited by the above examples, and the above examples and descriptions in the specification are only the principles of the utility model. Without departing from the spirit and scope of the utility model, the utility model can also have various changes and improvements, and these changes and improvements all fall within the scope of the utility model claimed. The protection scope required by the utility model is defined by the appended claims and their equivalents.

Claims

1. An aero-engine low-pressure turbine shaft radial carbon sealing ring dismounting tool, comprising a low-pressure turbine disc (1), characterized in that: The low-pressure turbine disc (1) is provided with a low-pressure turbine disc groove (2) in the inner center, a connecting flange (7) is arranged in the inner center of the low-pressure turbine disc groove (2), a low-pressure turbine disc front shaft (4) is arranged in the inner center of the connecting flange (7), a radial carbon sealing dynamic ring (3) is sleeved on the outer diameter of the low-pressure turbine disc front shaft (4), a circular pressure bearing flat plate (6) is abutted at the top end of the shaft surface of the low-pressure turbine disc front shaft (4), two claw pullers (5) are abutted at the top end of the outer surface of the circular pressure bearing flat plate (6), and a pulling force ring (8) is sleeved on the shaft surface of the low-pressure turbine disc groove (2).

2. The low pressure turbine shaft radial carbon seal ring dismounting tool of claim 1, wherein: M5 inner hexagonal cylindrical head screws (10) are inserted into the insertion slots of the pulling force ring (8), and fan-shaped connecting rings (9) are installed at the connecting positions of the outer surfaces of the pulling force ring (8).

3. The aero-engine low-pressure turbine shaft radial carbon sealing ring dismounting tool according to claim 1, characterized in that: The two claw pullers (5) comprise a hexagonal head screw rod (51), a base (52) and a pressing rod (55), the pressing rod (55) is installed at the bottom end of the outer surface of the hexagonal head screw rod (51), the base (52) is installed through the shaft surface of the pressing rod (55), the circular pressure bearing flat plate (6) is connected to the bottom end of the shaft surface of the pressing rod (55), and the outer surface of the base (52) is provided with a notch.

4. The aero-engine low-pressure turbine shaft radial carbon sealing ring dismounting tool of claim 3, wherein: The two claw pullers (5) further comprise a claw (53) and a bolt (54), the outer surface of the base (52) is provided with a notch, the claw (53) is arranged in the notch of the base (52), the bolt (54) is arranged on the outer surface of the base (52) opposite to the claw (53), the bottom end of the bolt (54) penetrates through the base (52) and is provided with a plug rod, and the plug rod penetrates through the claw (53).

5. The aero-engine low-pressure turbine shaft radial carbon sealing ring dismounting tool of claim 1, wherein: The pulling force ring (8) is composed of two semicircular ring plates, each semicircular ring plate has two ends, and each end has two M5 inner hexagonal cylindrical head screw thread through holes, a total of four M5 inner hexagonal cylindrical head screw thread through holes, and the two semicircular ring plates are connected to form the pulling force ring (8), and a total of eight M5 inner hexagonal cylindrical head screw thread through holes are arranged on the pulling force ring (8).

6. The low pressure turbine shaft radial carbon seal ring dismounting tool of claim 2, wherein: The fan-shaped connecting ring (9) is a fan ring plate, and a total of two fan-shaped connecting rings (9) are arranged, each fan-shaped connecting ring (9) is uniformly distributed with four M5 inner hexagonal cylindrical head screw thread through holes along the circumferential direction, the hole distance of the fan-shaped connecting ring (9) is the same as that of the pulling force ring (8), there are a total of eight M5 inner hexagonal cylindrical head screws (10) for connecting and fixing the fan-shaped connecting ring (9) and the pulling force ring (8).

7. The low pressure turbine shaft radial carbon seal ring dismounting tool of claim 2, wherein: The inner radius of the fan-shaped connecting ring (9) is R20.5, the outer radius of the fan-shaped connecting ring (9) is R28, the inner radius of the pulling force ring (8) is R18.95, the outer radius of the pulling force ring (8) is R25.95, and the radius of the connecting position of the outer surface of the pulling force ring (8) and the fan-shaped connecting ring (9) is R27.95.

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